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151. 发明授权

US06357236B1 Gas turbine, combined cycle plant and compressor 有权
标题翻译：燃气轮机，联合循环设备和压缩机
公开(公告)号：US06357236B1
公开(公告)日：2002-03-19
申请号：US09645402
申请日：2000-08-25
申请人： Motoaki Utamura
发明人： Motoaki Utamura
IPC分类号： F02C700
CPC分类号： F02C9/48 , F01K21/047 , F02C7/08 , F02C7/1435 , F04D29/5846 , F05D2270/053 , F05D2270/303 , Y02E20/14 , Y02E20/16 , Y02T50/675
摘要： A gas turbine, a combined cycle plant and compressor by which both augmentation of the power output and augmentation of the thermal efficiency can be realized by injecting liquid droplets into inlet air introduced into an entrance of a compressor with simple equipment which is suitable for practical use. The gas turbine includes a compressor for taking in and compressing gas, a combustor in which fuel is combusted with the gas discharged from the compressor, and a turbine driven by the combusted gas of the combustor. The gas turbine further includes a liquid droplet injection device provided on the upstream side of the compressor for injecting liquid droplets into inlet air to be supplied into the entrance of the compressor to lower the temperature of the inlet air to be introduced into the compressor so that the injected liquid droplets may be evaporated while flowing through the compressor.
摘要翻译：燃气轮机，联合循环设备和压缩机，其能够通过将液滴注入到具有适用于实际使用的简单设备的压缩机入口中的入口空气中来实现功率输出的增加和热效率的增加。燃气轮机包括用于吸入和压缩气体的压缩机，燃料与从压缩机排出的气体燃烧的燃烧器和由燃烧器的燃烧气体驱动的涡轮机。燃气轮机还包括液压喷射装置，其设置在压缩机的上游侧，用于将液滴注入入口空气中以供入压缩机的入口，以降低要引入压缩机的入口空气的温度，使得喷射的液滴可以在流过压缩机时蒸发。

152. 发明申请

US20020026783A1 Gas turbine, combined cycle plant and compressor 有权
标题翻译：燃气轮机，联合循环设备和压缩机
公开(公告)号：US20020026783A1
公开(公告)日：2002-03-07
申请号：US09960358
申请日：2001-09-24
申请人： Hitachi, Ltd.
发明人： Motoaki Utamura
IPC分类号： F02G003/00 , F02C001/00
CPC分类号： F02C9/48 , F01K21/047 , F02C7/08 , F02C7/1435 , F04D29/5846 , F05D2270/053 , F05D2270/303 , Y02E20/14 , Y02E20/16 , Y02T50/675
摘要： The invention provides a gas turbine, a combined plant and a compressor by which both of augmentation of the power output and augmentation of the thermal efficiency can be realized by injecting liquid droplets into inlet air introduced into an entrance of a compressor with a simple equipment which is suitable for practical use. The gas turbine includes a compressor for taking in and compressing gas, a combustor in which fuel is combusted with the gas discharged from the compressor, and a turbine driven by the combusted gas of the combustor. The gas turbine further includes a liquid droplet injection device provided on the upstream side of the compressor for injecting liquid droplets into inlet air to be supplied into the entrance of the compressor to lower the temperature of the inlet air to be introduced into the compressor so that the injected liquid droplets may be evaporated while flowing down in the compressor.
摘要翻译：本发明提供了一种燃气轮机，组合式设备和压缩机，通过该燃气轮机，组合式设备和压缩机，可以通过以简单的设备将液滴注入到引入压缩机入口的入口空气中来实现功率输出的增加和热效率的增加，适合实际使用。燃气轮机包括用于吸入和压缩气体的压缩机，燃料与从压缩机排出的气体燃烧的燃烧器和由燃烧器的燃烧气体驱动的涡轮机。燃气轮机还包括液压喷射装置，其设置在压缩机的上游侧，用于将液滴注入入口空气中以供入压缩机的入口，以降低要引入压缩机的入口空气的温度，使得喷射的液滴可以在压缩机中向下流动的同时蒸发。

153. 发明授权

US06216437B1 Method for regulating the power of a turbo set 有权
标题翻译：调节涡轮组功率的方法
公开(公告)号：US06216437B1
公开(公告)日：2001-04-17
申请号：US09153020
申请日：1998-09-15
申请人： Stephan Hepner , Hans-Kaspar Scherrer
发明人： Stephan Hepner , Hans-Kaspar Scherrer
IPC分类号： F02C900
CPC分类号： F02C9/54 , F01D17/04 , F01D17/06 , F05D2200/11 , F05D2270/053 , F05D2270/061 , F05D2270/304 , H02P9/04
摘要： In a method for regulating the power of a turbo set (10) converting thermal power into electric power, said turbo set (10) comprising, on a common shaft (17), a turbine (11) driven by the thermal power and a generator (16) driven by the turbine (11) and delivering electric power (PG) to a network (18), the electric power (PG) delivered by the generator (16) is determined and the thermal power (PT) for the turbine (11) is regulated as a function of the measured electric power (PG). Destabilization of the network and overloading of the turbo set (10) are avoided by additionally determining the kinetic power (Pkin) consumed or delivered by the shaft (17) and by regulating the thermal power (PT) in accordance with the sum of the electric power (PG) and kinetic power (Pkin).
摘要翻译：在一种用于调节将热功率转换成电力的涡轮机组（10）的功率的方法中，所述涡轮机组（10）包括在公共轴（17）上的由热力驱动的涡轮机（11）和发电机（16）由涡轮机（11）驱动并将电力（PG）输送到网络（18），确定由发电机（16）输送的电力（PG），并且确定涡轮机的热功率（PT） 11）作为测量电力（PG）的函数进行调节。通过另外确定由轴（17）消耗或输送的动能（Pkin）并且通过根据电气（17）的总和来调节热功率（PT）来避免网络的不稳定和涡轮组（10）的超载功率（PG）和动力（Pkin）。

154. 发明授权

US6098009A Method and device for controlling turbomachines 失效
标题翻译：用于控制涡轮机的方法和装置
公开(公告)号：US6098009A
公开(公告)日：2000-08-01
申请号：US956046
申请日：1997-10-22
申请人： Hans Wettstein
发明人： Hans Wettstein
IPC分类号： F01D17/00 , F02C9/00 , F02C9/28 , G05B9/03
CPC分类号： F02C9/28 , F05D2270/053
摘要： A method of controlling turbomachines is specified, a characteristic signal, in particular a performance signal, normally being fed to the controller as a controlled variable, but this performance signal, together with a number of further signals significant of the performance from the plant circuit, forming a signal set in a comparison and selection unit, and the signals from this signal set being compared with one another. The maximum selection among the signals, formed at the same time in the comparison and selection unit 2.1, yields the signal of the controlled variable that is forwarded to the controller 1.1. In addition, monitoring as to whether the performance signal is the maximum signal is performed. In addition, a device for controlling turbomachines according to the method is specified, which device has a control loop 1 for the output of actuating signals for control devices of the plant, the control loop 1 being preceded by a monitoring loop 2 that has a comparison and selection unit 2.1, to which, apart from the performance signal of the control loop 1, at least one further signal significant of the performance is additionally applied, and all these applied signals form a signal set. The comparison and selection unit 2.1 determines the maximum signal from these signal set and the said maximum signal is applied as input signal to a controller 1.1 of the control loop 1 in place of the direct performance signal.
摘要翻译：规定了一种控制涡轮机的方法，特征信号，特别是性能信号，通常作为受控变量馈送到控制器，但是该性能信号连同许多来自工厂电路的性能的进一步信号，在比较和选择单元中形成信号组，并将来自该信号组的信号彼此进行比较。在比较和选择单元2.1中同时形成的信号中的最大选择产生被转发到控制器1.1的受控变量的信号。此外，执行关于性能信号是否是最大信号的监视。此外，规定了根据该方法控制涡轮机的装置，该装置具有用于输出工厂控制装置的致动信号的控制回路1，控制回路1之前是具有比较的监控回路2 和选择单元2.1，除了控制回路1的执行信号之外，附加地施加至少一个对性能有重要影响的另外的信号，并且所有这些应用的信号形成信号组。比较选择单元2.1确定来自这些信号组的最大信号，并且将所述最大信号作为输入信号施加到控制回路1的控制器1.1以代替直接性能信号。

155. 发明授权

US5315819A Power management system for turbine engines 失效
标题翻译：涡轮发动机电力管理系统
公开(公告)号：US5315819A
公开(公告)日：1994-05-31
申请号：US762322
申请日：1991-09-17
申请人： George W. Page , Glen T. High , David L. Looper , James S. Frew , Larry C. Prevallet , Joseph W. Free
发明人： George W. Page , Glen T. High , David L. Looper , James S. Frew , Larry C. Prevallet , Joseph W. Free
IPC分类号： F02C9/28
CPC分类号： F02C9/28 , F05D2270/02 , F05D2270/051 , F05D2270/053 , Y02T50/671
摘要： A power management system for turbine engines includes a plurality of switches, each allowing for engine speed and engine torque to be controlled together. The switches correspond to various modes of operation of the turbine engine. When a switch is selected, a mode signal is supplied to a FADEC which, in response, issues speed and torque commands to an associated engine. The FADEC includes function generators that issue the torque commands as a function of outside ambient conditions. The torque commands are continuously updated for changing ambient conditions. Further, takeoff torque can be corrected for heating conditions. The power management system can also provide torque commands as a linear function of power lever angle.
摘要翻译：涡轮发动机的电力管理系统包括多个开关，每个开关允许一起控制发动机转速和发动机转矩。开关对应于涡轮发动机的各种操作模式。当选择开关时，模式信号被提供给FADEC，FADEC作为响应向相关联的发动机发出速度和扭矩命令。 FADEC包括发出扭矩指令作为外部环境条件的函数的函数发生器。不断更新扭矩指令以改变环境条件。此外，可以对加热条件校正起飞扭矩。电源管理系统还可以提供扭矩指令作为功率杆角度的线性功能。

156. 发明授权

US11967743B2 Modular fuel cell assembly 有权
公开(公告)号：US11967743B2
公开(公告)日：2024-04-23
申请号：US17676488
申请日：2022-02-21
申请人： General Electric Company
发明人： Honggang Wang , Radislav A. Potyrailo , Michael Anthony Benjamin
IPC分类号： F02C7/00 , B60L50/70 , B60L58/30 , B64D27/10 , B64D27/24 , H01M8/0444 , H01M8/04858 , H01M8/0662 , H01M8/249
CPC分类号： H01M8/0444 , B60L50/70 , B60L58/30 , B64D27/10 , B64D27/24 , F02C7/00 , H01M8/0494 , H01M8/0662 , H01M8/249 , B60L2200/10 , F05D2220/323 , F05D2240/35 , F05D2270/053 , H01M2250/20
摘要： A propulsion system is provided including: a gas turbine engine including a combustion section having a combustor; and a modular fuel cell assembly. The modular fuel cell assembly includes: a first fuel cell string comprising a first processing unit and a first fuel cell stack, the first fuel cell stack comprising a first fuel cell defining an outlet configured to provide output products from the first fuel cell to the combustor; and a second fuel cell string comprising a second processing unit and a second fuel cell stack, the second fuel cell stack comprising a second fuel cell defining an outlet configured to provide output products from the second fuel cell to the combustor.

157. 发明公开

US20230291278A1 GAS TURBINE ENGINE EQUIPPED WITH A CONTROL SYSTEM FOR MANAGEMENT OF ROTOR MODES USING AN ELECTRIC MACHINE 审中-公开
公开(公告)号：US20230291278A1
公开(公告)日：2023-09-14
申请号：US17488696
申请日：2021-09-29
申请人： General Electric Company , General Electric Deutschland Holding GmbH
发明人： Richard Schmidt , Darek Tomasz Zatorski , Rangasai Madoor Comandore , Mohamed Osama
IPC分类号： H02K7/18 , F01D15/10 , H02P9/00
CPC分类号： H02K7/1823 , F01D15/10 , H02P9/008 , F05D2270/053 , F05D2220/76 , B64D2027/026
摘要： A turbomachine is provided. In one aspect, the turbomachine includes a rotating component and an electric machine that includes a stator assembly and a rotor assembly rotatable with the rotating component relative to the stator assembly. Further, the turbomachine includes an actuator coupled with the rotor assembly, the stator assembly, or both for moving the rotor assembly, the stator assembly, or both relative to one another. In addition, the turbomachine includes a controller configured to receive data indicating an operating state of the rotating component and cause the actuator to adjust a position of at least one of the stator assembly and the rotor assembly based at least in part on the operating state of the rotating component.

158. 发明公开

US20230184179A1 AIRCRAFT PROPULSION SYSTEM 审中-公开
公开(公告)号：US20230184179A1
公开(公告)日：2023-06-15
申请号：US17941358
申请日：2022-09-09
申请人： ROLLS-ROYCE plc
发明人： Peter SWANN , Kevin M BRITCHFORD
IPC分类号： F02C9/42 , F02C9/28
CPC分类号： F02C9/42 , F02C9/28 , F05D2220/323 , F05D2270/051 , F05D2270/333 , F05D2270/335 , F05D2270/71 , F05D2270/053 , B64D2027/026
摘要： An aircraft propulsion system comprises first and second thrust producing gas turbine engines. The system comprises a controller configured to determine a required overall propulsion system thrust level, and determine an engine core power level contribution from each aircraft gas turbine engine such that the overall propulsion system produces a minimum overall noise level and meets the required overall propulsion system thrust level. In meeting the minimum overall noise level, at least the first and second gas turbine engines are operated at different engine core power settings.

159. 发明申请

US20190055901A1 METHOD AND SYSTEM FOR LIMITING POWER OF AN ENGINE 审中-公开
公开(公告)号：US20190055901A1
公开(公告)日：2019-02-21
申请号：US15681531
申请日：2017-08-21
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Sylvain LAMARRE , Simon LOPEZ , Nicolas DES ROCHES-DIONNE , Michael CONCIATORI
IPC分类号： F02K1/76 , F02K1/17 , F02C9/44 , F02K1/66
CPC分类号： F02K1/76 , B64C11/305 , F02C9/44 , F02C9/58 , F02K1/17 , F02K1/66 , F05D2270/053
摘要： Systems and methods for limiting power of a gas turbine engine for an aircraft are described herein. A blade angle of a propeller blade of the engine and a commanded power for the engine are obtained. A thrust transition direction is determined. The commanded power is compared to a selected threshold based on the blade angle and the thrust transition direction. Power to the engine is limited when the commanded power exceeds the selected threshold.

160. 发明申请

US20180080389A1 GAS TURBINE ENGINE WITH HEAT EXCHANGER DIAGNOSTICS 审中-公开
公开(公告)号：US20180080389A1
公开(公告)日：2018-03-22
申请号：US15271274
申请日：2016-09-21
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Frederick M. Schwarz , Nathan Snape
IPC分类号： F02C9/18 , F02C7/18
CPC分类号： F02C9/18 , F02C7/185 , F02K3/115 , F05D2260/213 , F05D2260/80 , F05D2270/053 , F05D2270/112 , F05D2270/301 , G01M15/09 , Y02T50/675
摘要： A gas turbine engine has a compressor section and a turbine section. A secondary cooling air includes a first fluid connection to tap cooling air and pass the cooling air through a plurality of tubes, and a second fluid connection for returning air from the tubes back to at least one of the compressor and turbine for cooling. A sensor senses a condition of the cooling air downstream of the tubes and a control compares the sensed condition of the cooling air to an expected condition, and to identify a potential concern in the cooling air system should the sensed condition differ from the expected condition by more than a predetermined amount.

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